DE102009040299A1 - Intake surface for rotor of turbo machine, particularly gas turbine, has profiled upper surface, which has multiple elongated, axially running recesses at distance from one another - Google Patents
Intake surface for rotor of turbo machine, particularly gas turbine, has profiled upper surface, which has multiple elongated, axially running recesses at distance from one another Download PDFInfo
- Publication number
- DE102009040299A1 DE102009040299A1 DE200910040299 DE102009040299A DE102009040299A1 DE 102009040299 A1 DE102009040299 A1 DE 102009040299A1 DE 200910040299 DE200910040299 DE 200910040299 DE 102009040299 A DE102009040299 A DE 102009040299A DE 102009040299 A1 DE102009040299 A1 DE 102009040299A1
- Authority
- DE
- Germany
- Prior art keywords
- axial direction
- rotor
- inlet lining
- depressions
- recesses
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Ceased
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Die Erfindung betrifft einen Einlaufbelag eines Rotors einer Strömungsmaschine, insbesondere einer Gasturbine, sowie einer Strömungsmaschine mit einem Rotor, an dem mehrere Schaufeln angeordnet sind.The invention relates to an inlet lining of a rotor of a turbomachine, in particular a gas turbine, as well as a turbomachine with a rotor, on which a plurality of blades are arranged.
Aus dem Stand der Technik sind Einlaufbeläge für Rotoren von Strömungsmaschinen bekannt, die eine wabenförmige Struktur aufweisen, wobei die Waben ein relativ weiches, abtragbares Material beinhalten.In the prior art, inlet linings for turbomachine rotors are known which have a honeycomb structure, the honeycombs including a relatively soft, abradable material.
Ferner ist es aus dem allgemeinen Stand der Technik bekannt, den Einlaufbelag als kompakte Schicht ohne Wabenstruktur aufzubringen.Furthermore, it is known from the general state of the art to apply the inlet lining as a compact layer without a honeycomb structure.
Aufgabe der Erfindung ist es, einen Einlaufbelag eines Rotors einer Strömungsmaschine zu schaffen, der eine aerodynamische Optimierung der Strömungsmaschine ermöglicht, sowie eine Strömungsmaschine mit einem solchen Einlaufbelag.The object of the invention is to provide an inlet lining of a rotor of a turbomachine, which enables an aerodynamic optimization of the turbomachine, as well as a turbomachine with such inlet lining.
Die Aufgabe der Erfindung wird durch einen Einlaufbelag eines Rotors einer Strömungsmaschine, insbesondere einer Gasturbine, mit einer profilierten Oberfläche gelöst, die eine Mehrzahl von nebeneinanderliegenden, umfangsmäßig beabstandeten, langgestreckten, axial verlaufenden Vertiefungen aufweist.The object of the invention is achieved by an inlet lining of a rotor of a turbomachine, in particular a gas turbine, with a profiled surface having a plurality of adjacent, circumferentially spaced, elongated, axially extending recesses.
Ein solcher strukturierter Einlaufbelag mit voneinander beabstandeten Vertiefungen, die in axialer Richtung und somit senkrecht zur Umlaufrichtung des Rotors verlaufen, ermöglicht eine Verbesserung der strömungstechnischen Eigenschaften der Strömungsmaschine. Die Erstreckung wird durch die Längsachse der Vertiefungen definiert.Such a structured inlet lining with spaced apart recesses, which extend in the axial direction and thus perpendicular to the direction of rotation of the rotor, allows an improvement of the fluidic properties of the turbomachine. The extent is defined by the longitudinal axis of the recesses.
Gemäß einer bevorzugten Ausführungsform weisen zumindest einige der Vertiefungen einen Boden auf, der sich in Axialrichtung unterschiedlich tief, d. h. radial unterschiedlich weit, in den Einlaufbelag erstreckt. Die Struktur des Einlaufbelags wird dadurch auch in radialer Richtung verändert.According to a preferred embodiment, at least some of the recesses have a bottom which varies in depth in the axial direction, d. H. radially differently far, extends into the inlet lining. The structure of the inlet lining is thereby also changed in the radial direction.
Vorzugsweise verlaufen die Vertiefungen in Axialrichtung zunehmend radial nach innen, insbesondere linear. Auf diese Weise können die Vertiefungen des Einlaufbelags gut an strömungstechnisch optimierte Schaufelspitzen angepasst werden, die beispielsweise in Axialrichtung linear zunehmend radial nach innen verlaufen.The recesses preferably extend increasingly radially inwards in the axial direction, in particular linearly. In this way, the recesses of the inlet lining can be adapted well to aerodynamically optimized blade tips, which extend linearly increasingly radially inwards, for example, in the axial direction.
Es ist möglich, dass die Vertiefungen in axialer Richtung eine sich ändernde umfangsmäßige Breite haben. Dies ermöglicht eine Variation der Einlaufbelagsstruktur in Umfangsrichtung.It is possible that the depressions have a varying circumferential width in the axial direction. This allows a variation of the inlet lining structure in the circumferential direction.
Die Breite der Vertiefungen in Umfangsrichtung kann, gemessen in Axialrichtung, abnehmen, insbesondere linear abnehmen.The width of the recesses in the circumferential direction, measured in the axial direction, decrease, in particular decrease linearly.
Gemäß einer bevorzugten Ausführungsform verlaufen die Vertiefungen in axialer Richtung konisch und vorzugsweise spitz zu.According to a preferred embodiment, the depressions extend conically and preferably pointedly in the axial direction.
Alternativ kann die Breite der Vertiefungen, in Umfangsrichtung gemessen, zumindest im, bezogen auf die Axialrichtung, mittleren Abschnitt konstant sein.Alternatively, the width of the recesses, measured in the circumferential direction, may be constant at least in the middle section relative to the axial direction.
Vorzugsweise verlaufen die Seitenwände der Vertiefungen ausschließlich in axialer und/oder radialer Richtung. Auf diese Weise bleiben die aerodynamischen Eigenschaften der Vertiefungen auch bei Abtrag des Einlaufbelags im Wesentlichen erhalten.Preferably, the side walls of the recesses extend exclusively in the axial and / or radial direction. In this way, the aerodynamic properties of the wells are essentially retained even when the enamel lining is removed.
Die obige Aufgabe wird auch durch eine Strömungsmaschine, insbesondere Gasturbine, gelöst, mit einem Rotor, an dem mehrere Schaufeln angeordnet sind, und einem oben beschriebenen Einlaufbelag, an dem die Schaufeln des Rotors anstreifen können.The above object is also achieved by a turbomachine, in particular a gas turbine, having a rotor on which a plurality of blades are arranged, and an inlet lining as described above, on which the blades of the rotor can rub against.
Vorzugsweise erstrecken sich die Vertiefungen in axialer Richtung über im Wesentlichen die gesamte axiale Länge der angrenzenden Schaufelspitzen des Rotors, um aerodynamisch auf den Rotor abgestimmt werden zu können.Preferably, the recesses extend in the axial direction over substantially the entire axial length of the adjacent blade tips of the rotor in order to be aerodynamically tuned to the rotor.
Die umfangsmäßige Breite der Vertiefungen kann größer sein als die größte Dicke der Schaufelspitze in Umfangsrichtung gemessen und/oder größer sein als der Abstand zwischen den Schaufelspitzen benachbarter Schaufeln des Rotors in Umfangsrichtung.The circumferential width of the recesses may be greater than the largest thickness of the blade tip measured in the circumferential direction and / or greater than the distance between the blade tips of adjacent blades of the rotor in the circumferential direction.
Vorzugsweise weisen die Schaufeln Schaufelspitzen auf, die, in Umfangsrichtung gesehen, in Axialrichtung zunehmend, insbesondere kontinuierlich, radial einwärts verlaufen.Preferably, the blades have blade tips which, seen in the circumferential direction, extend increasingly in the axial direction, in particular continuously, radially inwardly.
Weitere Merkmale und Vorteile der Erfindung ergeben sich aus der nachfolgenden Beschreibung und aus den nachfolgenden Zeichnungen, auf die Bezug genommen wird. In den Zeichnungen zeigen:Further features and advantages of the invention will become apparent from the following description and from the following drawings, to which reference is made. In the drawings show:
Die Oberfläche
In der gezeigten Ausführungsform ist jede Vertiefung
Die Vertiefungen
Der Boden
Die Breite der Vertiefungen
In den
Bei Betrieb der Strömungsmaschine können die Schaufeln mit den Schaufelspitzen
Die radiale Tiefe der Vertiefungen
In
In
Die Vertiefungen
Ringränder
In den
Auch die radiale Erstreckung des Bodens
Die Vertiefungen
In der in den
Im Folgenden wird die Funktion des Einlaufbelags
Im Einlaufbetrieb der Strömungsmaschine streifen die Schaufelspitzen
Durch die in radialer Richtung verlaufenden Seitenwände
BezugszeichenlisteLIST OF REFERENCE NUMBERS
- 1010
- Einlaufbelaginlet lining
- 1212
- Oberflächesurface
- 1414
- Vertiefungdeepening
- 1616
- SeitenwandSide wall
- 1818
- Bodenground
- 2020
- Schaufelspitzeblade tip
- 2222
- Ringrandannular rim
- SS
- Symmetrieachseaxis of symmetry
Claims (12)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200910040299 DE102009040299A1 (en) | 2009-09-04 | 2009-09-04 | Intake surface for rotor of turbo machine, particularly gas turbine, has profiled upper surface, which has multiple elongated, axially running recesses at distance from one another |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200910040299 DE102009040299A1 (en) | 2009-09-04 | 2009-09-04 | Intake surface for rotor of turbo machine, particularly gas turbine, has profiled upper surface, which has multiple elongated, axially running recesses at distance from one another |
Publications (1)
Publication Number | Publication Date |
---|---|
DE102009040299A1 true DE102009040299A1 (en) | 2011-03-10 |
Family
ID=43536108
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE200910040299 Ceased DE102009040299A1 (en) | 2009-09-04 | 2009-09-04 | Intake surface for rotor of turbo machine, particularly gas turbine, has profiled upper surface, which has multiple elongated, axially running recesses at distance from one another |
Country Status (1)
Country | Link |
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DE (1) | DE102009040299A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2013010529A1 (en) * | 2011-07-20 | 2013-01-24 | Mtu Aero Engines Gmbh | Method for producing an inlet lining, inlet system, turbomachine and guide blade |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2927724A (en) * | 1957-10-02 | 1960-03-08 | Avro Aircraft Ltd | Floating blade shrouds |
US3843278A (en) * | 1973-06-04 | 1974-10-22 | United Aircraft Corp | Abradable seal construction |
DE2703572A1 (en) * | 1976-01-30 | 1977-08-04 | Snecma | ABRASABLE STATUS SEAL FOR TURBO ENGINE |
DE69728898T2 (en) * | 1996-12-10 | 2005-04-28 | Chromalloy Gas Turbine Corp., San Antonio | A method of making a wearable seal, a wearable seal, and a gas turbine engine component having such a sealable seal |
DE60217456T2 (en) * | 2001-11-14 | 2007-11-08 | Snecma | Abradable coating for jacket rings of gas turbines |
EP2140973A1 (en) * | 2008-07-02 | 2010-01-06 | Huffman Corporation | Method and apparatus for selectively removing portions of an abradable coating using a water jet |
-
2009
- 2009-09-04 DE DE200910040299 patent/DE102009040299A1/en not_active Ceased
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2927724A (en) * | 1957-10-02 | 1960-03-08 | Avro Aircraft Ltd | Floating blade shrouds |
US3843278A (en) * | 1973-06-04 | 1974-10-22 | United Aircraft Corp | Abradable seal construction |
DE2703572A1 (en) * | 1976-01-30 | 1977-08-04 | Snecma | ABRASABLE STATUS SEAL FOR TURBO ENGINE |
DE69728898T2 (en) * | 1996-12-10 | 2005-04-28 | Chromalloy Gas Turbine Corp., San Antonio | A method of making a wearable seal, a wearable seal, and a gas turbine engine component having such a sealable seal |
DE60217456T2 (en) * | 2001-11-14 | 2007-11-08 | Snecma | Abradable coating for jacket rings of gas turbines |
EP2140973A1 (en) * | 2008-07-02 | 2010-01-06 | Huffman Corporation | Method and apparatus for selectively removing portions of an abradable coating using a water jet |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2013010529A1 (en) * | 2011-07-20 | 2013-01-24 | Mtu Aero Engines Gmbh | Method for producing an inlet lining, inlet system, turbomachine and guide blade |
US9840919B2 (en) | 2011-07-20 | 2017-12-12 | MTU Aero Engines AG | Method for producing a run-in coating, a run-in system, a turbomachine, as well as a guide vane |
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OM8 | Search report available as to paragraph 43 lit. 1 sentence 1 patent law | ||
R081 | Change of applicant/patentee |
Owner name: MTU AERO ENGINES AG, DE Free format text: FORMER OWNER: MTU AERO ENGINES GMBH, 80995 MUENCHEN, DE Effective date: 20130930 |
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R012 | Request for examination validly filed | ||
R002 | Refusal decision in examination/registration proceedings | ||
R003 | Refusal decision now final |